Work

Modeling and analysis of the TF30-P-3 compressor system with inlet pressure distortion

Year: 1976

Type: article

Abstract: Circumferential inlet distortion testing of a TF30-P-3 afterburning turbofan engine was conducted at NASA-Lewis Research Center. Pratt and Whitney Aircraft analyzed the data using its multiple segment parallel compressor model and classical compressor theory. Distortion attenuation analysis resulted in a detailed flow field calculation with good agreement between multiple segment model predictions and the test data. Sensitivity of the engine stall line to circumferential inlet distortion was calculated on the basis of parallel compressor theory to be more severe than indicated by the data. However, the calculated stall site location was in agreement with high response instrumentation measurements.

Source: NASA Technical Reports Server (NASA)

Authors: R. S. Mazzawy, G. A. Banks

Institution: Pratt & Whitney (United States)

Language: English

Topic: Turbomachinery Performance and Optimization

Subfield: Aerospace Engineering

Field: Engineering

Domain: Physical Sciences

Open Access status: green

Funder: National Aeronautics and Space Administration

OpenAlex ID: W753864091

FWCI:

Cites:

Cited by: 3

Related to: 10